69166 Federal Register / Vol. 76, No. 216 / Tuesday, November 8, 2011 / Proposed Rules 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 24 months after the effective 

date of this AD, modify the crossfeed valve 

control and power supply, the crossfeed 

indication logic and power supply, and the 

fuel fire shut-off valve indication logic, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–28–047, Revision 3, dated May 2, 

2011, including Fokker Manual Change 

Notification—Operational Documentation 

MCNO–F100–060, dated June 10, 2011, and 

Manual Change Notification—Operational 

Document MCNO–F100–049, Revision 1, 

dated May 30, 2011, including the drawings 

specified in paragraphs (g)(1) through (g)(15) 

of this AD. 

(1) Fokker Drawing D42770, Sheet 6, Issue 

U, dated May 2, 2011. 

(2) Fokker Drawing D42780, Sheet 6, Issue 

T, dated May 2, 2011. 

(3) Fokker Drawing W41074, Sheet 100, 

Issue GB, dated May 2, 2011. 

(4) Fokker Drawing W41074, Sheet 101, 

Issue FW, dated May 2, 2011. 

(5) Fokker Drawing W41194, Sheets 010 

and 012, Issue J, dated May 2, 2011. 

(6) Fokker Drawing W41194, Sheets 011, 

013, and 015, Issue U, dated May 2, 2011. 

(7) Fokker Drawing W41194, Sheets 014, 

019, and 020, Issue S, dated May 2, 2011. 

(8) Fokker Drawing W41194, Sheet 017, 

Issue Q, dated May 2, 2011. 

(9) Fokker Drawing W41319, Sheets 063, 

064, 065, 066, 069, 071, and 074, Issue DY, 

dated May 2, 2011. 

(10) Fokker Drawing W41319, Sheets 067, 

068, 070, 072, and 073, Issue DW, dated May 

2, 2011. 

(11) Fokker Drawing W46211, Sheet 71, 

Issue DL, dated April 21, 2009. 

(12) Fokker Drawing W46211, Sheet 74, 

Issue DN, dated July 16, 2010. 

(13) Fokker Drawing W46254, Sheets 30 

through 36, Issue BL, dated March 30, 2009; 

(14) Fokker Drawing W46254, Sheet 37, 

Issue BP, dated March 30, 2009. 

(15) Fokker Drawing W59221, Sheets 161 

and 162, Issue FC, July 9, 2010. 

(h) Before or concurrent with the 

modification specified in paragraph (g) of 

this AD, do the applicable actions specified 

in paragraphs (h)(1) and (h)(2) of this AD: 

(1) For all airplanes: Modify the overhead 

panel (introduce provisions for a modified 

crossfeed indication) in accordance with the 

Accomplishment Instructions of Fokker 

Profroma Service Bulletin SBF100–28–043, 

Revision 1, dated March 31, 2009, including 

Appendix II, Revision 2, dated July 22, 2010, 

including the drawings specified in 

paragraphs (h)(1)(i) through (h)(1)(iv) of this 

AD. 

(i) Fokker Drawing W41194, Sheet 009, 

Issue F, dated March 31, 2009. 

(ii) Fokker Drawing W41194, Sheet 016, 

Issue N, dated March 31, 2009. 

(iii) Fokker Drawing W41194, Sheet 018, 

Issue S, dated March 31, 2009. 

(iv) Fokker Drawing W59221, Sheet 159, 

Issue ED, dated October 2, 2009. 

(2) For airplanes with serial numbers 

11442 through 11585, equipped with the 

automatic fuel transfer system: Modify the 

transfer logic of the center wing fuel tank, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–28–052, including Fokker Manual 

Change Notification—Operational 

Documentation MCNO–F100–052 and 

Manual Change Notification—Maintenance 

Documentation MCNM–F100–126, dated 

June 15, 2009, including the drawings 

specified in paragraphs (h)(2)(i) through 

(h)(2)(v) of this AD. 

(i) Fokker Drawing D42126, Sheet 38, Issue 

AR, October 6, 1993. 

(ii) Fokker Drawing D42213, Sheet 2, Issue 

H, dated May 23, 1990. 

(iii) Fokker Drawing D42220, Sheet 60, 

Issue V, dated September 1, 1991. 

(iv) Fokker Drawing D42220, Sheet 71, 

Issue AQ, dated June 7, 1993. 

(v) Fokker Drawing D42250, Sheet 23, Issue 

U, dated April 1993. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(i) Modifications accomplished before the 

effective date of this AD according to the 

service bulletins specified in paragraphs 

(i)(1), (i)(2), (i)(3), and (i)(4) of this AD, as 

applicable, are considered acceptable for 

compliance with the corresponding action 

specified in this AD. 

(1) Fokker Service Bulletin SBF100–28– 

043, including Appendix II, dated March 31, 

2009. 

(2) Fokker Service Bulletin SBF100–28– 

047, Revision 2, dated August 4, 2010. 

(3) Fokker Service Bulletin SBF100–28– 

047, Revision 1, dated July 22, 2010. 

(4) Fokker Service Bulletin SBF100–28– 

047, dated May 10, 2010. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2010– 

0158R1, dated November 8, 2010; and the 

service bulletins specified in paragraphs (g) 

and (h) of this AD; for related information. 

Issued in Renton, Washington, on October 

28, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–28836 Filed 11–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1228; Directorate 

Identifier 2011–NM–176–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702), 

CL–600–2D15 (Regional Jet Series 705), 

CL–600–2D24 (Regional Jet Series 900), 

and CL–600–2E25 (Regional Jet Series 

1000) airplanes. This proposed AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

[I]t was found that the * * * ADG [air 

driven generator] GCU [generator control 

unit] transformer primary winding can break 

due to thermal fatigue. Broken transformer 

primary winding can prevent the supply of 

power from the ADG to the essential buses. 

In the event of an emergency, failure for the 

essential buses to remain powered can 

prevent continued safe flight. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

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Federal Register / Vol. 76, No. 216 / Tuesday, November 8, 2011 / Proposed Rules 69167 

DATES: We must receive comments on 

this proposed AD by December 23, 

2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

(514) 855–5000; fax (514) 855–7401; 

email thd.crj@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call (425) 227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7301; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–1228; Directorate Identifier 

2011–NM–176–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2011–27, 

dated July 25, 2011 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

There have been several occurrences of the 

air driven generator (ADG) failure to power 

essential buses during functional tests of the 

ADG on aeroplane models CL–600–2B16 and 

CL–600–2B19. The aeroplane models CL– 

600–2C10, CL–600–2D15, CL–600–2D24, and 

CL–600–2E25 use the same ADG generator 

control unit (GCU) as models CL–600–2B16 

and CL–600–2B19. However the aeroplane 

models CL–600–2C10, CL–600–2D15, CL– 

600–2D24, and CL–600–2E25 are installed 

with a different hydraulic pump and do not 

experience the same failure due to the low 

threshold setting of the circuit protection. 

However, it was found that the same ADG 

GCU transformer primary winding can break 

due to thermal fatigue. Broken transformer 

primary winding can prevent the supply of 

power from the ADG to the essential buses. 

In the event of an emergency, failure for the 

essential buses to remain powered can 

prevent continued safe flight. 

This [TCCA] directive mandates the 

replacement of the ADG GCU. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 670BA–24–031, dated May 30, 

2011. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 402 products of U.S. 

registry. We also estimate that it would 

take about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these parts. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $68,340, or $170 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

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69168 Federal Register / Vol. 76, No. 216 / Tuesday, November 8, 2011 / Proposed Rules 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Bombardier, Inc.: Docket No. FAA–2011– 

1228; Directorate Identifier 2011–NM– 

176–AD. 

Comments Due Date 

(a) We must receive comments by 

December 23, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1), (c)(2), and (c)(3) of this AD. 

(1) Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, serial numbers 10003 through 

10319 inclusive. 

(2) Bombardier, Inc. Model CL–600–2D15 

(Regional Jet Series 705) and CL–600–2D24 

(Regional Jet Series 900) airplanes, serial 

numbers 15001 through 15260 inclusive. 

(3) Bombardier, Inc. Model CL–600–2E25 

(Regional Jet Series 1000) airplanes, serial 

numbers 19001 through 19012 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

[I]t was found that the * * * ADG [air 

driven generator] GCU [generator control 

unit] transformer primary winding can break 

due to thermal fatigue. Broken transformer 

primary winding can prevent the supply of 

power from the ADG to the essential buses. 

In the event of an emergency, failure for the 

essential buses to remain powered can 

prevent continued safe flight. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 10,000 flight hours or 60 months 

after the effective date of this AD, whichever 

occurs first, remove the ADG GCU, part 

number (P/N) 604–90800–7, and install a 

new or serviceable ADG GCU, P/N 604– 

90800–27, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–24–031, dated May 

30, 2011. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install an ADG GCU, P/N 604– 

90800–7, on any airplane. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7300; fax (516) 

794–5531. Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(j) Refer to MCAI Canadian Airworthiness 

Directive CF–2011–27, dated July 25, 2011; 

and Bombardier Service Bulletin 670BA–24– 

031, dated May 30, 2011; for related 

information. 

Issued in Renton, Washington, on October 

31, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–28834 Filed 11–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1225; Directorate 

Identifier 2010–NM–269–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A300 B4–2C, B4–103, and 

B4–203 airplanes; Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model C4–605R Variant F airplanes 

(collectively called A300–600 series 

airplanes); and Model A310 series 

airplanes. This proposed AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

During a routine visual inspection on two 

A310 in-service aeroplanes, cracks were 

found in the wing MLG [main landing gear] 

rib 5 aft bearing forward lug. Laboratory 

examination of the cracked ribs confirmed 

that the cracks were the result of pitting 

corrosion in the forward lug hole. Also on 

both aeroplanes, medium to heavy corrosion 

was found in the forward lugs on the 

opposite wing after removal of the bushes. 

* * * This situation, if not corrected, could 

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